PMC laminate embedded hypotube lattice

Abstract

A gas turbine engine component such as a laminate airfoil having a static pressure transducer and having a plurality of structural fiber layers bonded with a polymer matrix composite. The transducer includes a lattice formed from a plurality of hypotubes aligned in a first direction and a plurality of reinforcing wires aligned substantially perpendicular to the hypotubes. The lattice is placed between at least some of the structural fiber layers prior to thermally processing into a cured polymer matrix laminate composite.

The invention claimed is: 
     
       1. A component of a gas turbine engine, the component comprising:
 a component body formed of a composite material; and 
 a hypotube lattice formed from a plurality of hypotubes aligned in a first direction having a plurality of reinforcing wires aligned substantially perpendicular to the hypotubes, the lattice being embedded within the component body with inlet ends exposed to fluid pressure and outlet ends of the hypotube lattice extending from the component to permit connection to pressure transducers. 
 
     
     
       2. The component of  claim 1 , wherein the hypotubes have an outer diameter from about 0.3 to about 0.4 mm. 
     
     
       3. The component of  claim 1 , wherein the device is embedded internally between layers of a laminate composite airfoil and the first direction is the radial direction of the airfoil. 
     
     
       4. The component of  claim 3 , wherein a grid work of holes in the laminate composite airfoil provide access to the hypotubes static pressure values. 
     
     
       5. The component of  claim 4 , wherein the plurality of hypotubes join together at one end of the air foil for transfer of static pressure therein. 
     
     
       6. The component of  claim 5 , wherein the laminate airfoil is formed by providing structural fiber layers bonded with a polymer matrix composite. 
     
     
       7. The component of  claim 6 , wherein the airfoil has a pressure side and suction side and a plurality of bundles of hypotubes are inserted in an airfoil on the pressure side. 
     
     
       8. A gas turbine engine component, the component comprising:
 a plurality of structural plies in polymeric matrix fiber layers bonded with a polymer matrix to form a laminate component; and 
 a lattice formed from a plurality of hypotubes aligned in a first direction and a plurality of reinforcing wires aligned substantially perpendicular to the hypotubes, the lattice being placed between at least some of the structural fiber layers composing a polymer matrix laminate composite, the plurality of hypotubes having an inlet end and an exit end. 
 
     
     
       9. The component of  claim 8 , wherein the hypotubes have an outer diameter from about 0.3 to about 0.4 mm. 
     
     
       10. The component of  claim 8 , wherein a grid work of holes are made in the laminate component to provide access to the inlet ends of the hypotubes for transfer of static pressure therein. 
     
     
       11. The component of  claim 10 , wherein the plurality of hypotubes join together at one end of the airfoil for transfer of static pressure therein. 
     
     
       12. The component of  claim 8 , wherein the plurality of hypotubes comprises a plurality of bundles of hypotubes such that each bundle of hypotubes has hypotubes of different lengths to present a spaced array of openings on the component. 
     
     
       13. The component of  claim 12 , wherein the component has an airfoil pressure side and suction side and a plurality of bundles of hypotubes are inserted on the airfoil pressure or suction side or both sides. 
     
     
       14. A method of measuring static pressure on an airfoil, the method comprising:
 positioning a plurality of hypotubes having an inlet end and an outlet end, the hypotubes being aligned in a first direction; 
 forming a lattice with a plurality of reinforcing wires aligned substantially perpendicular to the hypotubes, wherein the hypotubes produce a signal proportional to static pressure; and 
 placing the lattice inside an airfoil and connecting the hypotubes to the surface of the airfoil. 
 
     
     
       15. The method of  claim 14 , wherein the lattice is embedded internally between layers of a laminate composite airfoil and the first direction is the radial direction of the airfoil. 
     
     
       16. The method of  claim 15 , wherein the hypotubes have an outer diameter from about 0.3 to about 0.4 mm. 
     
     
       17. The method of  claim 14 , wherein a grid work of holes are made in the laminate airfoil to provide access to the inlet ends of the hypotubes. 
     
     
       18. The method of  claim 17 , wherein the plurality of hypotubes join together at one end of the air foil for transfer of static pressure therein. 
     
     
       19. The method of  claim 15 , wherein the laminate composite airfoil is formed by providing structural fiber layers bonded with a polymer matrix composite. 
     
     
       20. The method of  claim 19 , wherein the airfoil has a pressure side and suction side and a plurality of bundles of hypotubes are inserted in an airfoil on the airfoil pressure side, suction side, or both sides.